Determination of the critical velocity of a straight wing with a high aspect ratio

An aerodynamic problem on an air flow around a large aspect ratio rectangular wing is investigated in this study. According to the theory of Vlasov, considered be thin rod. External loads are assumed proportional airfoil angle attack related dimensionless coefficient lift and pitching moment coefficient. These coefficients depend parameters Mach number M determined by experimental measurements for subsonic supersonic velocities. In case, define unstable cases wing, one bases Lyapunov stability theory. Equations bending torsional free vibrations have resulted. Based analysis natural frequencies (eigenfrequencies), it possible determine changing positions real part imaginary characteristic equation solution. can cause instabilities such as divergence flutter.